RU2017136708A - REDUCER WITH EPICYCLOID TRANSMISSION FOR GAS TURBINE ENGINE - Google Patents

REDUCER WITH EPICYCLOID TRANSMISSION FOR GAS TURBINE ENGINE Download PDF

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Publication number
RU2017136708A
RU2017136708A RU2017136708A RU2017136708A RU2017136708A RU 2017136708 A RU2017136708 A RU 2017136708A RU 2017136708 A RU2017136708 A RU 2017136708A RU 2017136708 A RU2017136708 A RU 2017136708A RU 2017136708 A RU2017136708 A RU 2017136708A
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RU
Russia
Prior art keywords
reducer
axis
fastening
bearings
bodies
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RU2017136708A
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Russian (ru)
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RU2704516C2 (en
RU2017136708A3 (en
Inventor
Жереми Форла ЛАО
Оливье БЕЛЬМОНТ
Клементин Шарлотт Мари МУТОН
Тома Жюльен НГУЙЕН ВАН
Эмманюэль Пьер Димитри ПАТСУРИ
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Сафран Эркрафт Энджинз
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F16H57/082—Planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0467—Elements of gearings to be lubricated, cooled or heated
    • F16H57/0479—Gears or bearings on planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/048—Type of gearings to be lubricated, cooled or heated
    • F16H57/0482—Gearings with gears having orbital motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F16H2057/085—Bearings for orbital gears
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Claims (17)

1. Редуктор (11) с эпициклоидной передачей для газотурбинного двигателя (1), в частности, авиационного газотурбинного двигателя, содержащий:1. A reduction gear (11) with an epicycloid gear for a gas turbine engine (1), in particular, an aviation gas turbine engine, comprising: - планетарный вал (15) с осью А вращения,- a planetary shaft (15) with a rotation axis A, - коронную шестерню (19) с осью А, расположенную вокруг упомянутого планетарного вала (15),- ring gear (19) with axis A, located around the aforementioned planetary shaft (15), - сателлиты (18а,18b), распределенные вокруг упомянутой оси А, которые зацепляются с упомянутой коронной шестерней (19) и с планетарным валом (15), и- satellites (18a, 18b), distributed around said axis A, which engage with said ring gear (19) and the planetary shaft (15), and - держатель (17) сателлитов, содержащий, с одной стороны, органы (21) крепления подшипников (23а,23b) сателлитов (18а,18b), при этом органы крепления имеют осевую протяженность вдоль оси вращения В и равномерно распределены вокруг оси А, и, с другой стороны, деталь (20-38), поддерживающую каждый орган (21) крепления,- the holder (17) of the satellites, containing, on the one hand, the bodies (21) of fastening the bearings (23a, 23b) of the satellites (18a, 18b), while the attachment bodies have an axial length along the axis of rotation B and are evenly distributed around the axis A, on the other hand, the part (20-38) supporting each fastener (21), отличающийся тем, что деталь (20-38), поддерживающая каждый орган (21) крепления во существу в его середине вдоль его оси В, и упомянутые органы (21) крепления выполнены в виде единой детали со средствами (45,46,41) питания смазочным маслом упомянутых подшипников (23а,23b).characterized in that the part (20-38) supporting each fastening body (21) is essentially in its middle along its axis B, and the said fastening bodies (21) are made as a single part with means (45,46,41) of power lubricating oil of the said bearings (23a, 23b). 2. Редуктор (11) по п. 1, в котором средства (45,46,41) питания маслом упомянутых подшипников (23а,23b) выполнены в стенке органа (21) крепления.2. Reducer (11) according to claim 1, in which the means (45,46,41) for supplying oil to the said bearings (23a, 23b) are made in the wall of the fastening body (21). 3. Редуктор (11) по п. 1 или 2, в котором деталь (20-38) имеет ограниченную осевую протяженность, предусмотренную для ее размещения между подшипниками (23а,23b).3. Reducer (11) according to claim 1 or 2, in which the part (20-38) has a limited axial extent, provided for its placement between the bearings (23a, 23b). 4. Редуктор (11) по п. 1 или 2, в котором упомянутые органы (21) крепления имеют, каждый, полую трубчатую форму, предпочтительно с по существу круглым поперечным сечением на ее наружной периферии.4. The gearbox (11) of claim 1 or 2, in which said attachment bodies (21) have each a hollow tubular shape, preferably with a substantially circular cross section at its outer periphery. 5. Редуктор (11) по п.1 или 2, в котором упомянутые средства (45,46,41) питания смазочным маслом упомянутых подшипников (23а,23b) содержат по меньшей мере один наружный канал (41) циркуляции смазочного масла вокруг оси В, сообщающийся с наружной поверхностью упомянутых органов (21) крепления.5. Reducer (11) according to claim 1 or 2, in which said means (45,46,41) of lubricating oil supply for said bearings (23a, 23b) contain at least one outer channel (41) of lubricating oil circulation around axis B communicating with the outer surface of the mentioned organs (21) of attachment. 6. Редуктор (11) по одному из пп.1 или 2, в котором упомянутые органы (21) крепления выполнены в виде единой детали друг с другом и с трубчатым элементом (29) распределения смазочного масла, который расположен вокруг упомянутой оси А и который содержит кольцевую магистраль (37) распределения масла на органы (21) крепления.6. Reducer (11) according to one of claims 1 or 2, in which said attachment bodies (21) are made as a single part with each other and with a tubular element (29) of lubricating oil distribution, which is located around said axis A and contains an annular line (37) of oil distribution to the fastening organs (21). 7. Редуктор (11) по предыдущему пункту, в котором упомянутый трубчатый элемент (29) соединен одним из своих продольных концов с одним из продольных концов каждого из упомянутых органов (21) крепления.7. Reducer (11) according to the preceding paragraph, in which said tubular element (29) is connected by one of its longitudinal ends with one of the longitudinal ends of each of said attachment bodies (21). 8. Редуктор (11) по одному из пп.1 или 2, в котором каждый орган (21) крепления содержит две дорожки (22а,22b), каждая из которых выполнена с возможностью поддерживать по меньшей мере один подшипник (23а,23b) сателлита и которые имеют разные диаметры (D2,D1).8. Reducer (11) in one of claims 1 or 2, in which each attachment body (21) contains two lanes (22a, 22b), each of which is configured to support at least one satellite bearing (23a, 23b) and which have different diameters (D2, D1). 9. Редуктор (11) по одному из пп.1 или 2, в котором поддерживающая деталь (20,38) является деталью, отличной от органов (21) крепления.9. Reducer (11) according to one of claims 1 or 2, in which the supporting part (20.38) is a part different from the fastening organs (21). 10. Редуктор (11) по п.8, в котором поддерживающая деталь (20,38) содержит для каждого органа (21) крепления венец (38), окружающий его между двумя дорожками (22а,22b).10. Reducer (11) of claim 8, in which the supporting part (20.38) contains for each body (21) fastening a crown (38), surrounding it between the two tracks (22a, 22b). 11. Газотурбинный двигатель (1), отличающийся тем, что содержит по меньшей мере один редуктор (11) по одному из предыдущих пунктов.11. Gas turbine engine (1), characterized in that it contains at least one gear (11) in one of the preceding paragraphs. 12. Способ выполнения редуктора (11) по п. 10, отличающийся тем, что подшипники (23а,23b) и поддерживающую деталь (20,38) устанавливают на органах (21) крепления поступательными движениями одинакового направления вдоль осей В.12. The method for performing the gearbox (11) according to claim 10, characterized in that the bearings (23a, 23b) and the supporting part (20.38) are mounted on the fastening bodies (21) with translational movements of the same direction along the axes B.
RU2017136708A 2015-04-23 2016-04-21 Reduction gear with epicycloid transmission for gas turbine engine RU2704516C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1553675A FR3035375B1 (en) 2015-04-23 2015-04-23 EPICYCLOIDAL GEAR TRAIN REDUCER FOR A TURBOMACHINE.
FR1553675 2015-04-23
PCT/FR2016/050943 WO2017005997A2 (en) 2015-04-23 2016-04-21 Reduction gear having an epicyclic gear train for a turbine engine

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RU2017136708A true RU2017136708A (en) 2019-05-23
RU2017136708A3 RU2017136708A3 (en) 2019-09-30
RU2704516C2 RU2704516C2 (en) 2019-10-29

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US (1) US10302187B2 (en)
EP (1) EP3286457B1 (en)
JP (1) JP6768699B2 (en)
CN (1) CN107532518B (en)
BR (1) BR112017022476B1 (en)
CA (1) CA2982888C (en)
FR (1) FR3035375B1 (en)
RU (1) RU2704516C2 (en)
WO (1) WO2017005997A2 (en)

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Publication number Publication date
FR3035375B1 (en) 2018-07-27
CA2982888A1 (en) 2017-01-12
CN107532518B (en) 2019-09-10
RU2704516C2 (en) 2019-10-29
CN107532518A (en) 2018-01-02
RU2017136708A3 (en) 2019-09-30
WO2017005997A3 (en) 2017-03-23
EP3286457B1 (en) 2020-02-12
JP2018516331A (en) 2018-06-21
US10302187B2 (en) 2019-05-28
US20180163850A1 (en) 2018-06-14
CA2982888C (en) 2023-07-18
BR112017022476B1 (en) 2022-12-06
FR3035375A1 (en) 2016-10-28
EP3286457A2 (en) 2018-02-28
BR112017022476A2 (en) 2018-07-10
JP6768699B2 (en) 2020-10-14
WO2017005997A2 (en) 2017-01-12

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